RU2010129995A - GUIDING SYSTEM FOR THE TURBOREACTIVE ENGINE GONDOLA - Google Patents

GUIDING SYSTEM FOR THE TURBOREACTIVE ENGINE GONDOLA Download PDF

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Publication number
RU2010129995A
RU2010129995A RU2010129995/11A RU2010129995A RU2010129995A RU 2010129995 A RU2010129995 A RU 2010129995A RU 2010129995/11 A RU2010129995/11 A RU 2010129995/11A RU 2010129995 A RU2010129995 A RU 2010129995A RU 2010129995 A RU2010129995 A RU 2010129995A
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RU
Russia
Prior art keywords
gondola
nacelle
outer panel
air intake
middle section
Prior art date
Application number
RU2010129995/11A
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Russian (ru)
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RU2470839C2 (en
Inventor
Ги Бернар ВОШЕЛь (FR)
Ги Бернар ВОШЕЛЬ
Жан-Филипп ДОГЕ (FR)
Жан-Филипп ДОГЕ
Стефан БЕЙАР (FR)
Стефан БЕЙАР
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Эрсель (Fr)
Эрсель
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Publication of RU2010129995A publication Critical patent/RU2010129995A/en
Application granted granted Critical
Publication of RU2470839C2 publication Critical patent/RU2470839C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Jib Cranes (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

A nacelle includes a central structure intended to surround a fan of a turbojet engine and an air intake structure attached to the central structure and able to channel a flow of air toward the fan. The nacelle includes at least one longitudinal outer panel incorporating an air intake lip. An inner panel includes an acoustic shell ring which downstream end is attached to an upstream end of the central structure and therewith forms a fixed structure of the nacelle. Guide means are entirely attached to the central structure for guiding the outer panel or panels and allowing substantially rectilinear movement of the outer panel towards the upstream end of the nacelle so that the air intake structure can be opened.

Claims (17)

1. Гондола (1) турбореактивного двигателя, содержащая1. A nacelle (1) of a turbojet engine comprising воздухозаборную секцию (4), предназначенную для направления воздушного потока к вентилятору турбореактивного двигателя и содержащую по меньшей мере одну продольную наружную панель (40), объединенную с входной кромкой (4а),an air intake section (4) intended to direct the air flow to the turbofan engine fan and comprising at least one longitudinal outer panel (40) combined with the inlet edge (4a), среднюю секцию (5), расположенную вокруг указанного вентилятора, причем к средней секции прикреплена воздухозаборная секция (4) таким образом, что обеспечена аэродинамическая целостность,the middle section (5) located around the specified fan, and an air intake section (4) is attached to the middle section so that aerodynamic integrity is ensured, по меньшей мере одну внутреннюю панель (41), содержащую звукопоглощающую обечайку (53) и прикрепленную своим нижним по потоку концом (70) к верхнему по потоку концу (72) средней секции (5), причем в результате данного крепления образуется неподвижная конструкция гондолы (1), иat least one inner panel (41) containing a sound-absorbing shell (53) and attached with its downstream end (70) to the upstream end (72) of the middle section (5), and as a result of this fastening, a fixed structure of the nacelle ( 1), and направляющие средства (15), предназначенные для направления наружной панели (панелей) (40) и обеспечивающие, по существу, возможность прямолинейного перемещения наружной панели (40) к верхнему по потоку концу гондолы (1) с целью открытия воздухозаборной секции (4), отличающаяся тем, что направляющие средства (15) установлены исключительно на средней секции (5).guiding means (15) designed to guide the outer panel (s) (40) and providing essentially the possibility of rectilinear movement of the outer panel (40) to the upstream end of the nacelle (1) in order to open the air intake section (4), characterized the fact that the guide means (15) are installed exclusively on the middle section (5). 2. Гондола (1) по п.1, отличающаяся тем, что направляющие средства (15) установлены на корпусе (9) средней секции (5), причем указанный корпус (9) окружает вентилятор и обеспечивает аэродинамическую целостность совместно с внутренней панелью (41).2. A nacelle (1) according to claim 1, characterized in that the guiding means (15) are mounted on the housing (9) of the middle section (5), said housing (9) surrounding the fan and providing aerodynamic integrity together with the inner panel (41) ) 3. Гондола (1) по п.2, отличающаяся тем, что верхний по потоку конец (72) корпуса (9) содержит ряд отверстий, предназначенных для регулирования присоединения направляющих средств (15) и обеспечивающих установку направляющих средств (15) в заданном положении.3. The nacelle (1) according to claim 2, characterized in that the upstream end (72) of the housing (9) contains a number of holes designed to regulate the attachment of the guide means (15) and to ensure the installation of the guide means (15) in a predetermined position . 4. Гондола (1) по любому из пп.1-3, отличающаяся тем, что направляющие средства (15) содержат по меньшей мере одну систему рельсов (16, 32, 34, 47) и установочные средства (17, 20, 30, 31, 36, 45), предназначенные для установки наружной панели (панелей) (40) на систему (системы) рельсов (16, 23, 34, 47).4. Gondola (1) according to any one of claims 1 to 3, characterized in that the guiding means (15) comprise at least one rail system (16, 32, 34, 47) and mounting means (17, 20, 30, 31, 36, 45), designed to install the outer panel (s) (40) on the rail system (s) (16, 23, 34, 47). 5. Гондола (1) по п.4, отличающаяся тем, что по меньшей мере часть установочных средств (20) расположена ниже по потоку от участка (18), на котором средняя секция (5) и одна или более внутренняя панель (панели) (41) стыкуются в закрытом положении.5. Gondola (1) according to claim 4, characterized in that at least part of the installation means (20) is located downstream of the section (18), in which the middle section (5) and one or more internal panel (s) (41) join in the closed position. 6. Гондола (1) по п.4, отличающаяся тем, что установочные средства содержат по меньшей мере один ползунок (30, 31), выполненный с возможностью взаимодействия с по меньшей мере одним соответствующим рельсом (32).6. Gondola (1) according to claim 4, characterized in that the installation means comprise at least one slider (30, 31) configured to interact with at least one corresponding rail (32). 7. Гондола (1) по п.4, отличающаяся тем, что установочные средства содержат по меньшей мере одну систему линейных роликовых опор (45), выполненную с возможностью взаимодействия с соответствующим рельсом (47).7. Gondola (1) according to claim 4, characterized in that the installation means comprise at least one linear roller bearing system (45) configured to interact with a corresponding rail (47). 8. Гондола (1) по п.4, отличающаяся тем, что установочные средства содержат направляющую систему (36), выполненную с возможностью взаимодействия с по меньшей мере одним соответствующим желобчатым рельсом (34)8. Gondola (1) according to claim 4, characterized in that the installation means comprise a guide system (36) adapted to interact with at least one corresponding grooved rail (34) 9. Гондола (1) по п.4, отличающаяся тем, что направляющие средства (15) содержат по меньшей мере один продольный палец, выполненный с возможностью скольжения через соответствующее отверстие.9. The nacelle (1) according to claim 4, characterized in that the guiding means (15) comprise at least one longitudinal finger that is slidable through a corresponding hole. 10. Гондола (1) по любому из пп.1-3 или 5-9, отличающаяся тем, что направляющие средства (15) имеют полость (50), расположенную, по существу, поперек относительно оси (52) гондолы (1), причем указанная полость (50) находится ниже по потоку от внутренней панели (панелей) (41).10. Gondola (1) according to any one of claims 1 to 3 or 5-9, characterized in that the guiding means (15) have a cavity (50) located essentially transverse to the axis (52) of the nacelle (1), wherein said cavity (50) is located downstream of the inner panel (s) (41). 11. Гондола (1) по любому из пп.1-3 или 5-9, отличающаяся тем, что по меньшей мере одна наружная панель (40) содержит переднюю раму (90), выполненную с возможностью крепления к перегородке (92), составляющей одно целое с деталью (94), установленной на средней секции (5).11. Gondola (1) according to any one of claims 1 to 3 or 5-9, characterized in that at least one outer panel (40) comprises a front frame (90) configured to be attached to a partition (92) constituting integral with the part (94) mounted on the middle section (5). 12. Гондола (1) по п.11, отличающаяся тем, что перегородка (92) имеет отверстие, форма которого обеспечивает возможность прохождения через него направляющих средств (15).12. Gondola (1) according to claim 11, characterized in that the partition (92) has an opening, the shape of which allows passage of guiding means (15) through it. 13. Гондола (1) по п.11, отличающаяся тем, что перегородка (92) имеет выемку (100), форма которой соответствует по меньшей мере части (102) установочных средств (17), вследствие чего в закрытом положении установочные средства (17) обеспечивают воздухонепроницаемость перегородки (92).13. Gondola (1) according to claim 11, characterized in that the partition (92) has a recess (100), the shape of which corresponds to at least part (102) of the installation means (17), as a result of which the installation means (17) in the closed position ) provide airtightness to the partition (92). 14. Гондола (1) по любому из пп.1-3, 5-9 или 13, отличающаяся тем, что воздухозаборная секция (4) содержит средства с механическим или ручным управлением, предназначенные для сопровождения по меньшей мере одной наружной панели (40) вдоль направляющих средств (15).14. Gondola (1) according to any one of claims 1 to 3, 5-9 or 13, characterized in that the air intake section (4) contains means with mechanical or manual control, designed to accompany at least one outer panel (40) along the guiding means (15). 15. Гондола (1) по п.14, отличающаяся тем, что направляющие средства (15) содержат по меньшей мере один стопор, предназначенный для ограничения движения по меньшей мере одной наружной панели (40) и обеспечивающий возможность частичного открытия указанной наружной панели (панелей) (40).15. Gondola (1) according to claim 14, characterized in that the guiding means (15) comprise at least one stopper designed to restrict the movement of at least one outer panel (40) and allowing partial opening of said outer panel (s) ) (40). 16. Гондола (1) по любому из пп.1-3, 5-9 или 13, отличающаяся тем, что средняя секция (5) содержит средства центрирования и позиционирования направляющих средств (15).16. Gondola (1) according to any one of claims 1 to 3, 5-9 or 13, characterized in that the middle section (5) contains means for centering and positioning the guide means (15). 17. Гондола (1) по любому из пп.1-3, 5-9 или 13, отличающаяся тем, что воздухозаборная секция (4) содержит оборудование, предназначенное для предотвращения обледенения воздухозаборной секции (4). 17. Gondola (1) according to any one of claims 1 to 3, 5-9 or 13, characterized in that the air intake section (4) contains equipment designed to prevent icing of the air intake section (4).
RU2010129995/11A 2007-12-26 2008-09-10 System of guides for turbojet nacelle RU2470839C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR07/09105 2007-12-26
FR0709105A FR2925877B1 (en) 2007-12-26 2007-12-26 INSTALLATION OF GUIDING SYSTEM ON AN AIRCRAFT NACELLE.
PCT/FR2008/001262 WO2009080904A1 (en) 2007-12-26 2008-09-10 Aircraft nacelle guidance system installation

Publications (2)

Publication Number Publication Date
RU2010129995A true RU2010129995A (en) 2012-02-10
RU2470839C2 RU2470839C2 (en) 2012-12-27

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RU2010129995/11A RU2470839C2 (en) 2007-12-26 2008-09-10 System of guides for turbojet nacelle

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US (1) US8333344B2 (en)
EP (1) EP2222560B1 (en)
CN (1) CN101909998B (en)
AT (1) ATE535444T1 (en)
BR (1) BRPI0821023A2 (en)
CA (1) CA2705598A1 (en)
ES (1) ES2376701T3 (en)
FR (1) FR2925877B1 (en)
RU (1) RU2470839C2 (en)
WO (1) WO2009080904A1 (en)

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FR2925877B1 (en) 2009-12-04
EP2222560B1 (en) 2011-11-30
CN101909998B (en) 2013-04-24
RU2470839C2 (en) 2012-12-27
ATE535444T1 (en) 2011-12-15
WO2009080904A1 (en) 2009-07-02
CA2705598A1 (en) 2009-07-02
BRPI0821023A2 (en) 2015-06-16
CN101909998A (en) 2010-12-08
US20100252689A1 (en) 2010-10-07
ES2376701T3 (en) 2012-03-16
US8333344B2 (en) 2012-12-18
FR2925877A1 (en) 2009-07-03
EP2222560A1 (en) 2010-09-01

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